[go: up one dir, main page]

EP2920472A1 - Fastening means and attachment assembly - Google Patents

Fastening means and attachment assembly

Info

Publication number
EP2920472A1
EP2920472A1 EP12888502.7A EP12888502A EP2920472A1 EP 2920472 A1 EP2920472 A1 EP 2920472A1 EP 12888502 A EP12888502 A EP 12888502A EP 2920472 A1 EP2920472 A1 EP 2920472A1
Authority
EP
European Patent Office
Prior art keywords
fastening means
bolt
bushing
bolt portion
bore
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12888502.7A
Other languages
German (de)
French (fr)
Other versions
EP2920472B1 (en
EP2920472A4 (en
Inventor
Kjell Stenbom
Magnus BERGELIN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ums Skeldar Sweden AB
Original Assignee
Saab AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Saab AB filed Critical Saab AB
Publication of EP2920472A1 publication Critical patent/EP2920472A1/en
Publication of EP2920472A4 publication Critical patent/EP2920472A4/en
Application granted granted Critical
Publication of EP2920472B1 publication Critical patent/EP2920472B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B3/00—Key-type connections; Keys
    • F16B3/06—Key-type connections; Keys using taper sleeves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B7/00—Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections
    • F16B7/18—Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections using screw-thread elements
    • F16B7/182—Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections using screw-thread elements for coaxial connections of two rods or tubes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B13/00—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose
    • F16B13/12—Separate metal or non-separate or non-metal dowel sleeves fastened by inserting the screw, nail or the like
    • F16B13/124—Separate metal or non-separate or non-metal dowel sleeves fastened by inserting the screw, nail or the like fastened by inserting a threaded element, e.g. screw or bolt

Definitions

  • the fastening means or the attachment assemblies can, if the unwanted particles are not removed from the fastening means or the attachment assemblies, get damaged or broken. If the fastening means or the attachment assemblies are arranged in an aerial vehicle it is a disadvantage if the fastening means or the attachment assemblies get damaged or broken because it leads to decreasing operational safety of the aerial vehicle. If a rotor blade of an aerial vehicle is changed during maintenance of the aerial vehicle and unwanted particles enter between the fastening means and the bores passing through the rotor blade and wherein the fastening means is inserted, the bores of the rotor blade can get damaged. If the bores of a rotor blade get damaged it can lead to that the rotor blade has to be discarded, which also leads to a more time consuming and more expensive maintenance of the aerial vehicle.
  • the vibrations can result in component wear, for example bending or even breaking of the rotor blades, which in turn can result in an aerial vehicle crash.
  • US-Al-4961687 discloses a fastening device including sleeves for absorbing forces, and a rotor blade equipped with such a device for fastening to a hub.
  • the device comprises an inner metallic sleeve having a cylindrical central bore and having a frusto-conical outer lateral face which is pressed coaxially and is affixed in the frusto-conical inner bore of an outer sleeve provided with a slot along one of its generatrices, and fitted into a recess delimited in the blade root by a loop formed of bands of rovings of the spar of the blade.
  • the fitting of the two sleeves into one another involves a deformation by radial expansion of the outer sleeve, which adapts itself to the diameter of the recess provided in the composite materials of the blade root.
  • the invention applies to helicopter rotor blades.
  • the fastening means and attachment assembly that are disclosed in the document US-Al- 4961687 has a drawback.
  • the conical sleeves in document US-Al-4961687 surround both the part of the bolt which abuts the rotor hub and the part of the bolt which abuts the rotor blade. This results in that the hole in the rotor blade must be larger or that the diameter of the bolt must be smaller, which leads to a too weaker construction.
  • the fastening means comprises a bolt having a first bolt portion, a second bolt portion and an intermediate bolt portion arranged between the first bolt portion and the second bolt portion.
  • the first bolt portion is conical and the second bolt portion is threaded.
  • the fastening means further comprises a first bushing with a conical inner surface arranged in circumferential abutment to the first bolt portion and a nut to be thread- edly engaged to the second bolt portion.
  • the first bushing has a cylindrical outer surface.
  • the fastening means comprises an intermediate bushing arranged in circumferential abutment to the intermediate bolt portion.
  • the intermediate bolt portion is cylindrical and the intermediate bushing has a cylindrical inner surface.
  • the intermediate bushing has a cylindrical outer surface.
  • the fastening means comprises a sleeve arranged in circumferential abutment to the second bolt portion.
  • the second bolt portion can be cylindrical and the sleeve may have a cylindrical inner surface.
  • the fastening means comprises a second bushing arranged in circumferential abutment to the sleeve.
  • the sleeve can have a conical outer surface and the second bushing can have a conical inner surface.
  • the second bushing has a cylindrical outer surface.
  • the second bolt portion is provided with a locking element.
  • the fastening means and the attachment assembly comprises few parts compared to prior art and all these parts have smooth surfaces in abutment to each other. It is therefore difficult for unwanted particles, such as dust, grit and contaminants, to enter between the parts. This results in turn to less time consuming and less expensive maintenance of the fastening means and attachment assembly. If the fastening means or attachment assembly is arranged in an aerial vehicle, for example a helicopter, a less time consuming maintenance is an advantage because it leads to that the time for service of the aerial vehicle decreases and in turn the aerial vehicles availability increases. If the fastening means or attachment assembly is arranged in an aerial vehicle it is also an advantage that the risk of the fastening means or attachment assembly getting damaged or broken decrease because it leads to increasing operational safety of the aerial vehicle.
  • the attachment assembly according to the present invention comprises few parts with smooth surfaces in abutment to each other the play between the parts is limited. This results in decreasing vibrations and in turn decreasing component wear. If the attachment assembly is arranged in an aerial vehicle with a rigid or semi rigid rotor system the movement in the horizontal plane is decreased and in turn the risk of an aerial vehicle crash is decreased.
  • the fastening means and the attachment assembly com- prise a bolt with a conical head and a conical bushing in circumferential abutment to the conical head. Because the head is conical it is self centred when inserted into the conical bushing. Therefore the fastening means and the attachment assembly are easier to assemble, disassemble and reassemble compared to fastening means and attachment assemblies comprising a bolt with a cylindrical head and a cylindrical bushing in circumferential abutment to the cylindri- cal head. Because the fastening means and the attachment assembly are easier to assemble the parts comprised in the fastening means and the attachment assembly can have less tight tolerances. Therefore the use of a master fixture or co-boring of the bores comprised in the attachment assembly is not needed. This results in a less time consuming and less expensive production.
  • the conical sleeve in the attachment assembly only surrounds the head of the bolt.
  • the remainder of the bolt and the bushings in circumferential abutment to the remainder of the bolt are cylindrical. This results in that the bores in which the bushings in circumferential abutment to the remainder of the bolt are inserted do not have to be larger or that the diameter of the bolt does not have to be smaller, which leads to a stronger construction.
  • Fig. IB shows a perspective view of an attachment assembly, wherein one fastening means is exploded, according to prior art
  • Fig. IB shows a perspective view of an attachment assembly 18, wherein one fastening means 1 is exploded, according to prior art.
  • the respective fastening means 1 comprise the same features as shown in fig. 1A and that are described above. These features have the same reference numbers as in fig. 1A.
  • the respective fastening means 1 is also arranged inside two bores 14 passing through a second object 20, for example a rotor blade.
  • the respective nut 8 fastens the cylindrical bolt 2, the cylindrical bushing 4, the washers 6, the first object 16 and the second object 20 together. By tightening the nut 8 the attachment assembly 18 can be readily assembled, disassembled and reassembled.
  • Fig. 2 shows a cross sectional view of a fastening means 22 according to the present invention.
  • the fastening means comprises a bolt 24.
  • the bolt 24 comprises a first bolt portion 26, a second bolt portion 28 and an intermediate bolt portion 30.
  • the first bolt portion 26, also called head, is arranged opposed to the second bolt portion 28.
  • the intermediate bolt portion 30 is arranged between the first bolt portion 26 and the second bolt portion 28.
  • the first bolt portion 26 is constituted by a head in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and wherein the base is arranged in the end of the bolt 24.
  • the second bolt portion 28 and the intermediate portion 30 are cylindrical.
  • the second bolt portion 28 comprises a threaded portion 32, with threads along the threaded portions 32 length, arranged in the end of the bolt 24.
  • a first bushing 34 is arranged in circumferential abutment to the first bolt portion 26.
  • the first bushing 34 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the first bolt portion 26.
  • An intermediate bushing 36 comprising a cylindrical inner and outer surface, is arranged in circumferential abutment to the intermediate bolt portion 30.
  • a sleeve 38 is arranged in circumferential abutment to the second bolt portion 28 and inside a second bushing 56.
  • the intermediate bushing 36 is in substantial abutment with the intermediate bolt portion 30 along the whole abutment surface between the intermediate bushing 36 and the intermediate bolt por- tion 30.
  • the sleeve 38 is in substantial abutment with the second bolt portion 28 along the whole abutment surface between the sleeve 38 and the second bolt portion 28.
  • the second bushing 56 is in substantial abutment with the sleeve 38 along the whole abutment surface between the second bushing 56 and the sleeve 38. It is therefore difficult for unwanted particles to enter between the parts. This results in that the time for keeping the fastening means 22 clean from unwanted particles, such as dust, grit and contaminants, decreases.
  • fastening means 22 are arranged in an aerial vehicle, for example a helicopter, it is an advantage with less time consuming maintenance of the fastening means 22 because it leads to that the time for service of the aerial vehicle decreases and in turn the aerial vehicles availability increases. If the fastening means 22 are arranged in an aerial vehicle it is an advantage that the fastening means 22 do not get damaged or broken due to unwanted particles entering between the different parts because it leads to increasing operational safety of the aerial vehicle.
  • Each rotor blade 50 is fitted in one end with a fastening means 22 for connection to a respec- tive arm of the rotor hub 58. More specifically, the rotor hub 58 is typically C-shaped with a first protruding arm 46 and a second protruding arm 54, a recess 60 between the arms 46 and 54 and a rotor blade 50 arranged in the recess 60. The first protruding arm 46 and the second protruding arm 54 are parallel to each other.
  • the rotor hub 58 is joined and affixed to at least two rotor blades 50, preferably in a rigid or semi rigid rotor system.
  • a first bushing 34 is arranged in circumferential abutment to the first bolt portion 26 and inside a first bore 44 passing through a first object 46, for example a rotor hub 58.
  • the first bushing 34 can be arranged inside the first bore 44 by pressing the first bushing 34 into the first bore 44.
  • the first bushing 34 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the first bolt portion 26.
  • a locking element 40 is arranged through respective threaded bolt portion 32, at the end of the bolt 24.
  • the locking element 40 is not required, but it is advantageous that the attachment assembly 42 comprise the locking element 40 when the attachment assembly 42 is used in applications where vibration or rotation can make the nut 8 disappear from the threaded bolt portion 32. It is possible to use various locking elements, for example a cotter pin.
  • first bushing 34 is in substantial abutment with the first bore portion 44 along the whole abutment surface between the first bushing 34 and the first bore portion 44
  • the intermediate bushing 36 is in substantial abutment with the intermediate bore portion 48 along the whole abutment surface between the intermediate bushing 36 and the intermediate bore portion 48
  • the second bushing 56 is in substantial abutment with the second bore portion 52 along the whole abutment surface between the second bushing 56 and the second bore portion 52.
  • the attachment assembly 42 therefore has the same advantages as the fastening means 22 described above. Yet another advantage is that the discard of parts comprised in the attachment assembly 42, for example rotor blades 50, decreases.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Connection Of Plates (AREA)

Abstract

The present invention relates to a fastening means (22) and an attachment assembly (42). The fastening means (22) comprises a bolt (24) having a first bolt portion (26), a second bolt portion (28) and an intermediate bolt portion (30) arranged between the first bolt portion (26) and the second bolt portion (28). The first bolt portion (26) is conical and the second bolt portion (28) is threaded. The fastening means (22) further comprises a first bushing (34) with a conical inner surface arranged in circumferential abutment to the first bolt portion (26) and a nut (8) to be threadedly engaged to the second bolt portion (28). The attachment assembly (42) for securing objects (46, 50, 54) to each other comprises at least two bores, arranged through the objects, comprising a first bore portion (44), a second bore portion (52) and an intermediate bore portion (48), respectively. The intermediate bore portion (48) is arranged between the first bore portion (44) and the second bore portion (52). The attachment assembly also com- prises at least two fastening means (22), each of the fastening means (22) being arranged inside the bores, respectively.

Description

Fastening means and attachment assembly
TECHNICAL FIELD The present invention relates to a fastening means according to the preamble of claim 1. The invention also relates to an attachment assembly.
TECHNICAL BACKGROUND Fastening means of the type that mechanically joins and affixes two or more objects together are used in a wide range of applications, for example automobiles and aerial vehicles. Fastening means on the market today, for example core bolts inserted in clamping sleeves, comprise many parts and these parts often do not comprise smooth surfaces. Attachment assemblies comprise two or more objects mechanically joined and affixed together by such fastening means and are used in a wide range of applications, for example automobiles and aerial vehicles. Attachment assemblies on the market today, each for example comprising a rotor hub, rotor blades and fastening means, comprise many parts and these parts often do not comprise smooth surfaces. Because the parts comprised in the fastening means and in the attachment assemblies do not comprise smooth surfaces a large portion of their surfaces are not in abutment to each other. It is therefore easy for unwanted particles to enter between the parts. This result in that it is difficult and time consuming to keep the fastening means and the attachment assemblies clean from unwanted particles such as dust, grit and contaminants. This results in turn to more ex- pensive maintenance of the fastening means and the attachment assemblies. If the fastening means or the attachment assemblies are arranged in an aerial vehicle, for example a helicopter, it is a disadvantage that it is time consuming to keep the fastening means and the attachment assemblies clean because it leads to that the time for service of the aerial vehicle increases and in turn the aerial vehicles availability decreases. In worst case the fastening means or the attachment assemblies can, if the unwanted particles are not removed from the fastening means or the attachment assemblies, get damaged or broken. If the fastening means or the attachment assemblies are arranged in an aerial vehicle it is a disadvantage if the fastening means or the attachment assemblies get damaged or broken because it leads to decreasing operational safety of the aerial vehicle. If a rotor blade of an aerial vehicle is changed during maintenance of the aerial vehicle and unwanted particles enter between the fastening means and the bores passing through the rotor blade and wherein the fastening means is inserted, the bores of the rotor blade can get damaged. If the bores of a rotor blade get damaged it can lead to that the rotor blade has to be discarded, which also leads to a more time consuming and more expensive maintenance of the aerial vehicle.
As described earlier, attachment assemblies comprise objects being joined and affixed to each other and often a bolt inserted in bores passing through these objects. It will be impossible to mount the bolt in the bores if the bores through the different objects, for example through a rotor blade and through a rotor hub, are not aligned. One solution could be to increase the diameter of the bores or decrease the core diameter of the bolt to fit some existing expandable fastener or similar, but that would be a disadvantage because it will result in a weaker construction with greater play between the attachment assembly's components. To ensure that the bores are made to the correct specifications and therefore are aligned they need to be co-bored or a master fixture needs to be used. A master fixture is however expensive to manufacture because it is built to fit a particular object. Co-boring of holes leads to a more time consuming and a more expensive production. A rotor system substantially comprises a rotor hub connected to a rotor drive shaft, and a number of rotor blades fixed to and projecting radially from the rotor hub. Each rotor blade is fitted in one end with a fastening means for connection to a respective arm of the hub. More specifically, the end of the hubs arm is typically C-shaped with opposite parallel end portions connected releasable to one end of the respective rotor blade. Rotor systems are classified according to how the rotor blades are attached and move relative to the rotor hub. There are three basic classifications: rigid, semi rigid or fully articulated rotor systems. In a fully articulated rotor system, each rotor blade is attached to the rotor hub through a series of hinges which allow the blade to move independently of the others. Dampers are usually used in articulated rotor systems to prevent excess back and forth movement. Rigid and semi rigid rotor systems do not permit the rotor blades to move, relative to the rotor hub, back and forth slightly in the horizontal plane because the back-and-forth hunting can develop into serious unwanted vibrations. The terms "dragging," "hunting," and "lead-lag" are also used to describe this movement. The vibrations can result in component wear, for example bending or even breaking of the rotor blades, which in turn can result in an aerial vehicle crash. To de- crease the movement back and forth in the horizontal plane the play in the attachment between the rotor blades and the rotor hub is limited by using components with tight tolerances. It is however expensive to manufacture components with tight tolerances because machining and inspection of the components are time consuming and the component rejection rate in- creases. Even if the components have tight tolerances it is difficult to achieve an attachment between the rotor blades and the rotor hub with limited play because the several tolerances need to cooperate with each other.
Another example of a known fastening means and attachment assembly are disclosed in document US-Al-4961687. US-Al-4961687 discloses a fastening device including sleeves for absorbing forces, and a rotor blade equipped with such a device for fastening to a hub. The device comprises an inner metallic sleeve having a cylindrical central bore and having a frusto-conical outer lateral face which is pressed coaxially and is affixed in the frusto-conical inner bore of an outer sleeve provided with a slot along one of its generatrices, and fitted into a recess delimited in the blade root by a loop formed of bands of rovings of the spar of the blade. The fitting of the two sleeves into one another involves a deformation by radial expansion of the outer sleeve, which adapts itself to the diameter of the recess provided in the composite materials of the blade root. The invention applies to helicopter rotor blades. The fastening means and attachment assembly that are disclosed in the document US-Al- 4961687 has a drawback. The conical sleeves in document US-Al-4961687 surround both the part of the bolt which abuts the rotor hub and the part of the bolt which abuts the rotor blade. This results in that the hole in the rotor blade must be larger or that the diameter of the bolt must be smaller, which leads to a too weaker construction.
As a consequence, in light of the above drawbacks, there is a need of a fastening means and an attachment means which are less time consuming and less expensive to produce, easier to maintain, and an attachment means with a strong construction which avoid lateral vibrations. SUMMARY OF THE INVENTION
The subject of the present invention is to eliminate the drawbacks according to prior art. This subject has been by fulfilled with the fastening means as well as the attachment assembly according to the claims. More specifically the fastening means comprises a bolt having a first bolt portion, a second bolt portion and an intermediate bolt portion arranged between the first bolt portion and the second bolt portion. The first bolt portion is conical and the second bolt portion is threaded. The fastening means further comprises a first bushing with a conical inner surface arranged in circumferential abutment to the first bolt portion and a nut to be thread- edly engaged to the second bolt portion.
In another aspect of the invention the first bushing has a cylindrical outer surface. In a further aspect of the invention the fastening means comprises an intermediate bushing arranged in circumferential abutment to the intermediate bolt portion. In yet another aspect of the invention the intermediate bolt portion is cylindrical and the intermediate bushing has a cylindrical inner surface. In another aspect of the invention the intermediate bushing has a cylindrical outer surface. In a further aspect of the invention the fastening means comprises a sleeve arranged in circumferential abutment to the second bolt portion. Further, the second bolt portion can be cylindrical and the sleeve may have a cylindrical inner surface. In another aspect of the invention the fastening means comprises a second bushing arranged in circumferential abutment to the sleeve. In addition the sleeve can have a conical outer surface and the second bushing can have a conical inner surface. In yet another aspect of the invention the second bushing has a cylindrical outer surface. In another aspect of the invention the second bolt portion is provided with a locking element.
The attachment assembly for securing objects to each other comprises at least two bores, arranged through the objects, comprising a first bore portion, a second bore portion and an in- termediate bore portion, respectively. The intermediate bore portion is arranged between the first bore portion and the second bore portion. The attachment assembly also comprises at least two fastening means of the kind described above according to the invention, each arranged inside the bores, respectively. In another aspect of the invention the objects to be secured comprise a rotor hub having a first protruding arm, a second protruding arm and a recess between the arms. A rotor blade is arranged in the recess. The first bore portion is extending through the first protruding arm, the intermediate bore portion is extending through the rotor blade and the second bore portion is extending through the second protruding arm. The fastening means and the attachment assembly according to the present invention comprises few parts compared to prior art and all these parts have smooth surfaces in abutment to each other. It is therefore difficult for unwanted particles, such as dust, grit and contaminants, to enter between the parts. This results in turn to less time consuming and less expensive maintenance of the fastening means and attachment assembly. If the fastening means or attachment assembly is arranged in an aerial vehicle, for example a helicopter, a less time consuming maintenance is an advantage because it leads to that the time for service of the aerial vehicle decreases and in turn the aerial vehicles availability increases. If the fastening means or attachment assembly is arranged in an aerial vehicle it is also an advantage that the risk of the fastening means or attachment assembly getting damaged or broken decrease because it leads to increasing operational safety of the aerial vehicle.
Because the attachment assembly according to the present invention comprises few parts with smooth surfaces in abutment to each other the play between the parts is limited. This results in decreasing vibrations and in turn decreasing component wear. If the attachment assembly is arranged in an aerial vehicle with a rigid or semi rigid rotor system the movement in the horizontal plane is decreased and in turn the risk of an aerial vehicle crash is decreased.
The fastening means and the attachment assembly according to the present invention com- prise a bolt with a conical head and a conical bushing in circumferential abutment to the conical head. Because the head is conical it is self centred when inserted into the conical bushing. Therefore the fastening means and the attachment assembly are easier to assemble, disassemble and reassemble compared to fastening means and attachment assemblies comprising a bolt with a cylindrical head and a cylindrical bushing in circumferential abutment to the cylindri- cal head. Because the fastening means and the attachment assembly are easier to assemble the parts comprised in the fastening means and the attachment assembly can have less tight tolerances. Therefore the use of a master fixture or co-boring of the bores comprised in the attachment assembly is not needed. This results in a less time consuming and less expensive production.
As described above, the conical sleeve in the attachment assembly only surrounds the head of the bolt. The remainder of the bolt and the bushings in circumferential abutment to the remainder of the bolt are cylindrical. This results in that the bores in which the bushings in circumferential abutment to the remainder of the bolt are inserted do not have to be larger or that the diameter of the bolt does not have to be smaller, which leads to a stronger construction.
Other objectives, embodiments and advantages of the present invention are described in closer detail in the description and in the subsequent patent claims.
BRIEF DESCRIPTION OF THE DRAWINGS
In the following prior art and the invention will be described with reference to embodiments of prior art, embodiments of the present invention and the accompanying drawings, in which:
Fig. 1A shows a perspective view of two fastening means, wherein one fastening means is exploded, according to prior art,
Fig. IB shows a perspective view of an attachment assembly, wherein one fastening means is exploded, according to prior art,
Fig. 2 shows a cross sectional view of a fastening means according to the present invention, and
Fig. 3 shows a cross sectional view of an attachment assembly according to the present invention.
DETAILED DESCRIPTION OF PRIOR ART AND THE INVENTION
In the following a number of embodiments of prior art and the invention are shown and described. The same reference numbers have been used for the same or similar features throughout the description in the embodiments disclosed below.
Fig. 1A shows a perspective view of two fastening means 1, wherein one fastening means 1 is exploded, according to prior art. The respective fastening means 1 comprise a cylindrical bolt 2, for example a fitting bolt, a cylindrical bushing 4, arranged in circumferential abutment to the cylindrical bolt 2, two washers 6, arranged in circumferential abutment to the cylindrical bushing 4 and a nut 8.The respective cylindrical bolt 2 comprise a head 10 and a threaded portion 12, with threads along the threaded portions 12 length, arranged opposed to the head 10. The respective nut 8, having internal threads matching the threads of the threaded portion 12, is arranged on the threaded portion 12 to fasten the cylindrical bolt 2, the cylindrical bushing 4 and the washers 6 together. The respective fastening means 1 is arranged inside two bores 14 passing through a first object 16, for example a rotor hub. By tightening the nut 8 the fastening means 1 can be assembled disassembled and reassembled.
Fig. IB shows a perspective view of an attachment assembly 18, wherein one fastening means 1 is exploded, according to prior art. The respective fastening means 1 comprise the same features as shown in fig. 1A and that are described above. These features have the same reference numbers as in fig. 1A. The respective fastening means 1 is also arranged inside two bores 14 passing through a second object 20, for example a rotor blade. The respective nut 8 fastens the cylindrical bolt 2, the cylindrical bushing 4, the washers 6, the first object 16 and the second object 20 together. By tightening the nut 8 the attachment assembly 18 can be readily assembled, disassembled and reassembled.
Fig. 2 shows a cross sectional view of a fastening means 22 according to the present invention. The fastening means comprises a bolt 24. The bolt 24 comprises a first bolt portion 26, a second bolt portion 28 and an intermediate bolt portion 30. The first bolt portion 26, also called head, is arranged opposed to the second bolt portion 28. The intermediate bolt portion 30 is arranged between the first bolt portion 26 and the second bolt portion 28. The first bolt portion 26 is constituted by a head in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and wherein the base is arranged in the end of the bolt 24. The second bolt portion 28 and the intermediate portion 30 are cylindrical. The second bolt portion 28 comprises a threaded portion 32, with threads along the threaded portions 32 length, arranged in the end of the bolt 24.
A first bushing 34 is arranged in circumferential abutment to the first bolt portion 26. The first bushing 34 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the first bolt portion 26. An intermediate bushing 36, comprising a cylindrical inner and outer surface, is arranged in circumferential abutment to the intermediate bolt portion 30. A sleeve 38 is arranged in circumferential abutment to the second bolt portion 28 and inside a second bushing 56. The sleeve 38 comprises a cylindrical inner surface and a conical outer surface, wherein the conical outer surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the end of the bolt 24. The second bushing 56 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the sleeves 38 outer surface.
A nut 8, having internal threads matching the threads of the threaded portion 32, is arranged on the threaded portion 32 to fasten the bolt 24, the first bushing 34, the intermediate bushing 36 and the sleeve 38 together. By tightening the nut 8 the fastening means 22 can readily be assembled, disassembled and reassembled. The nut 8 can be constituted by a wide range of different types of nuts, for example a castle nut or a locking nut. A locking element 40 is arranged through the second threaded bolt portion 32, at the end of the bolt 24. It is advanta- geous that the fastening means 22 comprise the locking element 40 when the fastening means 22 is used in applications where vibration or rotation can make the nut 8 disappear. It is possible to use various locking elements 40, for example a cotter pin.
The bolt 24, the first bushing 34, the intermediate bushing 36, the sleeve 38, the locking ele- ment 40 and the nut 8 can be made of many different types of materials and they can have different lengths, thicknesses and finishes. The fastening means 22 according to the present invention can be used in a wide range of applications, for example automobiles and aerial vehicles. The parts comprised in the fastening means 22 all have smooth surfaces in abutment to each other. The first bushing 34 is in substantial abutment with the first bolt portion 26 along the whole abutment surface between the first bushing 34 and the first bolt portion 26. The intermediate bushing 36 is in substantial abutment with the intermediate bolt portion 30 along the whole abutment surface between the intermediate bushing 36 and the intermediate bolt por- tion 30. The sleeve 38 is in substantial abutment with the second bolt portion 28 along the whole abutment surface between the sleeve 38 and the second bolt portion 28. The second bushing 56 is in substantial abutment with the sleeve 38 along the whole abutment surface between the second bushing 56 and the sleeve 38. It is therefore difficult for unwanted particles to enter between the parts. This results in that the time for keeping the fastening means 22 clean from unwanted particles, such as dust, grit and contaminants, decreases. In turn it results to less expensive and less time consuming maintenance of the fastening means 22. If the fastening means 22 are arranged in an aerial vehicle, for example a helicopter, it is an advantage with less time consuming maintenance of the fastening means 22 because it leads to that the time for service of the aerial vehicle decreases and in turn the aerial vehicles availability increases. If the fastening means 22 are arranged in an aerial vehicle it is an advantage that the fastening means 22 do not get damaged or broken due to unwanted particles entering between the different parts because it leads to increasing operational safety of the aerial vehicle.
Fig. 3 shows a cross sectional view of an attachment assembly 42 according to the present invention. The attachment assembly 42, such as for example a rotor blade and hub attachment assembly, comprises a fastening means 22, a first object 46, an intermediate object 50 and a second object 54. The respective fastening means 1 comprise the same features as shown in fig. 2 and that are described above. These features have the same reference numbers as in fig. 2. A rotor system substantially comprises a rotor hub 58 connected angularly to a rotor drive shaft, and a number of rotor blades 50 fixed to and projecting radially from the rotor hub 58. Each rotor blade 50 is fitted in one end with a fastening means 22 for connection to a respec- tive arm of the rotor hub 58. More specifically, the rotor hub 58 is typically C-shaped with a first protruding arm 46 and a second protruding arm 54, a recess 60 between the arms 46 and 54 and a rotor blade 50 arranged in the recess 60. The first protruding arm 46 and the second protruding arm 54 are parallel to each other. The rotor hub 58 is joined and affixed to at least two rotor blades 50, preferably in a rigid or semi rigid rotor system.
A first bushing 34 is arranged in circumferential abutment to the first bolt portion 26 and inside a first bore 44 passing through a first object 46, for example a rotor hub 58. The first bushing 34 can be arranged inside the first bore 44 by pressing the first bushing 34 into the first bore 44. The first bushing 34 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the first bolt portion 26. An intermediate bushing 36, comprising a cylindrical inner and outer surface, is arranged in circumferential abutment to the intermediate bolt portion 30 and inside an intermediate bore 48 passing through an intermediate object 50, for example a rotor blade 50. An advantageous positional tolerance for the intermediate bushing 36 and the bolt 24 can be H5 or G5. The intermediate bushing 36 can be integrated to the inside of the intermediate bore 48, by for example moulding. A sleeve 38 is arranged in circumferential abutment to the second bolt portion 28 and inside a second bushing 56. The sleeve 38 comprises a cylindrical inner surface and a conical outer surface, wherein the conical outer surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the end of the bolt 24. The second bushing 56 comprises a cylindrical outer surface and a conical inner surface, wherein the conical inner surface is in the form of a frustum of a cone with a top and a base, wherein the top is arranged opposed to the base and the base is arranged in circumferential abutment to the base of the sleeves 38 outer surface. The second bushing 56 is arranged inside a second bore 52 passing through a second object 54.
The first bore 44, the intermediate bore 48 and the second bore 52 does not need to be totally concentric depending on the outcome of the tolerances. The pitch between the first bore 44 and the intermediate bore 48, the pitch between the intermediate bore 48 and the second bore 52 and the pitch between the first bore 44 and the second bore 52 can be for example 0.1 mm. Because the first bore 44, the intermediate bore 48 and the second bore 52 does not need to be totally concentric they do not need to be co-bored and a master fixture is not needed. This leads to a less expensive and less time consuming production of the attachment assembly 42. The first bore 44, the intermediate bore 48 and the second bore 52 can suitably have a diameter of about 6-50 mm.
A nut 8, having internal threads matching the threads of the threaded portion 32, is arranged on the threaded portion 32 to fasten the bolt 24, the first bushing 34, the intermediate bushing 36, the sleeve 38, the second bushing 56, the first object 46, the intermediate object 50 and the second object 54 together. Because the first bolt portion 26 has a conical outer surface it is self centered when it is inserted into the first bushing 34 with a conical inner surface. By tightening the nut 8 the fastening means 22 can therefore readily be assembled, disassembled and reassembled. The nut 8 can be constituted by a wide range of different types of nuts, for example a castle nut or a locking nut.
A locking element 40 is arranged through respective threaded bolt portion 32, at the end of the bolt 24. The locking element 40 is not required, but it is advantageous that the attachment assembly 42 comprise the locking element 40 when the attachment assembly 42 is used in applications where vibration or rotation can make the nut 8 disappear from the threaded bolt portion 32. It is possible to use various locking elements, for example a cotter pin.
The bolt 24, the first bushing 34, the intermediate bushing 36, the sleeve 38, the second bush- ing 56, the locking element 40 and the nut 8 can be made of many different types of materials and they can have different lengths, thicknesses and finishes. The attachment assembly 42 is not limited to comprise three objects (in this embodiment a first object 46, an intermediate object 50 and a second object 54); it can comprise a large plurality of objects. As described above, all the parts comprised in the fastening means 22 have smooth surfaces in abutment to each other. Also the first bushing 34 is in substantial abutment with the first bore portion 44 along the whole abutment surface between the first bushing 34 and the first bore portion 44, the intermediate bushing 36 is in substantial abutment with the intermediate bore portion 48 along the whole abutment surface between the intermediate bushing 36 and the intermediate bore portion 48 and the second bushing 56 is in substantial abutment with the second bore portion 52 along the whole abutment surface between the second bushing 56 and the second bore portion 52. The attachment assembly 42 therefore has the same advantages as the fastening means 22 described above. Yet another advantage is that the discard of parts comprised in the attachment assembly 42, for example rotor blades 50, decreases.
The invention is not limited by what has been particularly shown or described, except as indicated by the appended claims.

Claims

1. A fastening means (22), comprising a bolt (24) having a first bolt portion (26), a second bolt portion (28) and an intermediate bolt portion (30) arranged between the first bolt portion (26) and the second bolt portion (28), where the first bolt portion (26) is conical and the second bolt portion (28) is threaded, further comprising a first bushing (34) arranged in circumferential abutment to the first bolt portion (26), and a nut (8) to be threadedly engaged to the second bolt portion (28),
characterized in that
the first bushing (34) has a conical inner surface.
2. The fastening means according to claim 1, wherein the first bushing (34) has a cylindrical outer surface.
3. The fastening means according to claim 1 or 2, comprising an intermediate bushing (36) arranged in circumferential abutment to the intermediate bolt portion (30).
4. The fastening means according to claim 3, wherein the intermediate bolt portion (30) is cylindrical and wherein the intermediate bushing (36) has a cylindrical inner surface.
5. The fastening means according to claim 3 or 4, wherein the intermediate bushing (36) has a cylindrical outer surface.
6. The fastening means according to any of the previous claims, comprising a sleeve (38) ar- ranged in circumferential abutment to the second bolt portion (28).
7. The fastening means according to claim 6, wherein the second bolt portion (28) is cylindrical and the sleeve (38) has a cylindrical inner surface.
8. The fastening means according to claim 6 or 7, comprising a second bushing (56) arranged in circumferential abutment to the sleeve (38).
9. The fastening means according to claim 8, wherein the sleeve (38) has a conical outer surface and the second bushing (56) has a conical inner surface.
10. The fastening means according to claim 8 or 9, wherein the second bushing (56) has a cylindrical outer surface.
11. The fastening means according to any of the previous claims, wherein the second bolt portion (28) is provided with a locking element (40).
12. An attachment assembly (42) for securing objects (46, 50, 54) to each other, comprising at least two bores, arranged through the objects (46, 50, 54), each bore comprising a first bore portion (44), a second bore portion (52) and an intermediate bore portion (48), respectively, the intermediate bore portion (48) is arranged between the first bore portion (44) and the second bore portion (52), and at least two fastening means (22) according to one or more of claims 1-11, each of the fastening means (22) being arranged inside the bores (44, 48, 52), respectively.
13. The attachment assembly (42) according to claim 12, wherein the objects (46, 50, 54) to be secured comprises a rotor hub (58) having a first protruding arm (46) and a second protruding arm (54), a recess (60) between the arms (46, 54) and a rotor blade (50) arranged in the recess (60), the first bore portion (44) is extending through the first protruding arm (46), the intermediate bore portion (48) is extending through the rotor blade (50) and the second bore portion (52) is extending through the second protruding arm (54).
EP12888502.7A 2012-11-14 2012-11-14 Fastening means and attachment assembly Active EP2920472B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2012/051255 WO2014077744A1 (en) 2012-11-14 2012-11-14 Fastening means and attachment assembly

Publications (3)

Publication Number Publication Date
EP2920472A1 true EP2920472A1 (en) 2015-09-23
EP2920472A4 EP2920472A4 (en) 2016-07-06
EP2920472B1 EP2920472B1 (en) 2017-08-02

Family

ID=50731528

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12888502.7A Active EP2920472B1 (en) 2012-11-14 2012-11-14 Fastening means and attachment assembly

Country Status (4)

Country Link
US (1) US20150308473A1 (en)
EP (1) EP2920472B1 (en)
ES (1) ES2645753T3 (en)
WO (1) WO2014077744A1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10570949B2 (en) * 2016-03-17 2020-02-25 The Boeing Company Damage tolerant and fail-safe (DTFS) high strength preloaded pin assembly
US10480566B2 (en) * 2016-03-17 2019-11-19 The Boeing Company Damage tolerant and fail-safe (DTFS) high strength preloaded pin assembly
CN206407129U (en) * 2016-12-27 2017-08-15 昊翔电能运动科技(昆山)有限公司 Unmanned plane oar seat lock paddle structure
US20210221536A1 (en) * 2019-11-21 2021-07-22 Volansi, Inc. Drone assembly hanger

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1667610A (en) * 1927-04-12 1928-04-24 John W Tewsley Wear-compensating pin
US3460628A (en) * 1961-11-06 1969-08-12 Bendix Corp Laminated tension-torsion tie-bar
US3271058A (en) * 1963-05-22 1966-09-06 Anderson Greenwood & Co Tapered fastener
US3298725A (en) * 1964-10-01 1967-01-17 John C Boteler High-strength fastener
US3603626A (en) * 1969-01-27 1971-09-07 Standard Pressed Steel Co High-strength joint and fastener assembly therefor
US3584473A (en) * 1969-11-19 1971-06-15 Uniroyal Inc Force-transmitting systems
US3835615A (en) * 1970-04-30 1974-09-17 J King Fastener joint construction
US4048898A (en) * 1974-10-17 1977-09-20 Paul R. Briles Fastener for multi metal stack-ups
FR2620178B1 (en) * 1987-09-09 1990-01-19 Aerospatiale SOCKET FASTENER, AND ROTOR BLADE PROVIDED WITH SUCH A HUB FASTENER
NZ221163A (en) * 1988-01-22 1991-07-26 Bruce Archibald Short Tapered resilient bush for vehicle suspension arm
US4869632A (en) * 1988-03-02 1989-09-26 United Technologies Corporation Bolted connection for a turbine disk
US5521951A (en) * 1994-09-23 1996-05-28 General Electric Company Reactor core shroud repair with tapered pins
US5682678A (en) * 1995-11-13 1997-11-04 The Nordam Group, Inc. Mechanical repair for a honeycomb panel
US7665969B2 (en) * 2005-01-24 2010-02-23 Bell Helicopter Textron Inc. Assembly for providing flexure to blade system
DE102006058140B4 (en) * 2006-03-22 2009-06-10 Airbus Deutschland Gmbh bolt connection
DE102006000413A1 (en) * 2006-08-23 2008-02-28 Hilti Ag expansion anchor
US7695226B2 (en) * 2006-09-21 2010-04-13 Alcoa Global Fasteners, Inc. High performance sleeved interference fasteners for composite applications
DE102007044404A1 (en) * 2007-09-18 2009-03-19 P&S Vorspannsysteme Ag Connecting arrangement or connection method with all-sided adhesion
US8262331B2 (en) * 2009-05-04 2012-09-11 Polaris Fastening Consulting, Llc Integrated expanding sleeve hole filling threaded fastener

Also Published As

Publication number Publication date
ES2645753T3 (en) 2017-12-07
US20150308473A1 (en) 2015-10-29
EP2920472B1 (en) 2017-08-02
EP2920472A4 (en) 2016-07-06
WO2014077744A1 (en) 2014-05-22

Similar Documents

Publication Publication Date Title
CN115989369B (en) Aircraft turbine engine comprising variable pitch propeller blades
EP2726301B1 (en) Attachment arrangement for composite wheels
EP2920472B1 (en) Fastening means and attachment assembly
CA2686988C (en) Guide vane architecture
EP2921727B1 (en) U-shaped clip for fixing a link rod within an aircraft clevis
US9475576B2 (en) Flexbeam rotor attachment to rotor blade
CN101557910A (en) Hub device
EP2914868B1 (en) Axle-mounted brake disc with a connecting element
CN115885109A (en) Aircraft turbine engine including variable pitch propeller blades
CN112867607A (en) Wheel of vehicle
US20130129445A1 (en) Tie bar for purposes of connecting equipment fitting of an equipment module, in particular an overhead compartment, to a structure fitting of a fuselage cell structure of an aeronautical vehicle
US9102413B2 (en) Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle
RU2655897C2 (en) Construction structure for blade and jet engine including such structure
US9315275B2 (en) Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle
US11981418B2 (en) System for controlling the pitch setting of a propeller vane for an aircraft turbine engine
DK2772432T3 (en) Rotorfly pitch beam attachment with anti-rotation plate design
EP2247502B1 (en) A de-icer, a fixture and a method of adjusting the position of a de-icer
EP2993305B1 (en) Gas turbine
WO2021020053A1 (en) Vehicular wheel
CN221942954U (en) Nut mounting structure, wheel hub and commercial vehicle
CN105020278B (en) Axially coupled component, linkage and aircraft
US8926245B2 (en) Assembly comprising a device for locking a fastening
WO2024084095A1 (en) An axial fan and methods of manufacturing axial fan blades and assembling the fan
CN120813776A (en) Holding portion for one or more rotating assembly elements, in particular wheels for aircraft landing gear
CN104120932A (en) Quick-release thread lock

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20150506

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAX Request for extension of the european patent (deleted)
RA4 Supplementary search report drawn up and despatched (corrected)

Effective date: 20160607

RIC1 Information provided on ipc code assigned before grant

Ipc: B64C 27/48 20060101ALI20160601BHEP

Ipc: F16B 5/02 20060101AFI20160601BHEP

Ipc: F16B 3/06 20060101ALI20160601BHEP

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UMS SKELDAR SWEDEN AB

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20170227

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 914818

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170815

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012035512

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170802

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2645753

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20171207

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171102

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171103

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171202

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171102

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012035512

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

26N No opposition filed

Effective date: 20180503

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20171114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171114

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20171130

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171114

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171130

REG Reference to a national code

Ref country code: AT

Ref legal event code: UEP

Ref document number: 914818

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20121114

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230525

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20241016

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: AT

Payment date: 20241017

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20250114

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20250919

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20250915

Year of fee payment: 14